Abstract
An approach based on indicial concepts is described to model the unsteady airloads on a thin airfoil in subsonic compressible flow caused by the arbitrary motion of a trailing-edge flap. Exact indicial aerodynamic responses at small values of time as a result of flap deflection and angular deflection rate about the flap hinge are obtained from linear unsteady subsonic theory in conjunction with the aerodynamic reverse flow theorems. Using the known exact initial (piston theory) and asymptotic values of the airloads, along with an assumed analytic form for the indicial functions, these exact results are used to help obtain complete approximations for the respective indicial responses. The airloads from arbitrary flap motion in subsonic flow are subsequently obtained in state - space form. Validation of the method is conducted with experimental data for time-dependent flap motions.
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